{"id":"F2006L02513","name":"AD/F50/95 - Passenger Service Units","slug":"ad-f50-95-passenger-service-units","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":59739,"registerId":"commonwealth-F2006L02513-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Fokker F50 (F27 Mk 50) Series Aeroplanes","sectionType":"division","heading":"Fokker F50 (F27 Mk 50) Series Aeroplanes","content":"### Fokker F50 (F27 Mk 50) Series Aeroplanes\n\n| AD/F50/95 | Passenger Service Units | 9/2006 |\n| --------- | ----------------------- | ------ |\n\n| Applicability: | F27 Mark 050 and 0502 aeroplanes equipped with Honeywell International (Grimes Aerospace) Passenger Service Units (PSU) part number (P/N) 10-1178-XX.                                                                                                                                                                                                                                                                                             |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Inspect the affected PSU (P/N 10-1178-XX series) panel interface connectors in accordance with Section 3 - Accomplishment Instructions of Fokker Service Bulletin SBF50-25-061 dated 31 March 2006 or later EASA approved revision.                                                                                                                                                                                                            |\n|                | 2. If, as a result of the Requirement 1 inspection, any discrepancies are found, rectify the discrepancy in accordance with Section 3 - Accomplishment Instructions of SBF50-25-061 or later EASA approved revision.                                                                                                                                                                                                                              |\n|                | Note: CAA-NL AD NL-2006-008 (EASA Approval 2006-0193) refers.                                                                                                                                                                                                                                                                                                                                                                                     |\n| Compliance:    | For Requirement 1 - Within 36 months after the effective date of this Directive.                                                                                                                                                                                                                                                                                                                                                                  |\n|                | For Requirement 2 - Before further flight after the Requirement 1 inspection.                                                                                                                                                                                                                                                                                                                                                                     |\n|                | This Airworthiness Directive becomes effective on 31 August 2006.                                                                                                                                                                                                                                                                                                                                                                                 |\n| Background:    | The Netherlands Civil Aviation Authority (CAA-NL) has advised that recently, a Fokker 100 (F28 Mark 0100) operator noted that the electrical connectors of the PSUs did not lock properly during installation in the aircraft.                                                                                                                                                                                                                    |\n|                | Investigation revealed that the lack of locking is caused by the tolerance in thickness of the gaskets (seals) inside the PSU connectors. This condition, if not corrected, may cause the connector to overheat, leading to electrical arcing and subsequent failure of the PSU Panels. In such instances, smoke is likely to be emitted. To rectify and prevent this occurring, the PSU manufacturer has narrowed the tolerances of the gaskets. |\n\n|     | PSU panels installed in Fokker 50 (F27 Mark 050 and Mark 0502) aircraft are similar to those installed in the Fokker 100 and since an unsafe condition has been identified that is likely to exist or develop on aircraft of these type designs, this Directive requires inspection and, where necessary, replacement of the affected PSU Panel J1 and J2 interface connector gaskets. |\n| --- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n21 July 2006","sortOrder":0},{"sectionNumber":"AD/F50/95","sectionType":"part","heading":"AD/F50/95","content":"## AD/F50/95","sortOrder":1},{"sectionNumber":"Passenger Service Units","sectionType":"part","heading":"Passenger Service Units","content":"## Passenger Service Units","sortOrder":2},{"sectionNumber":"9/2006","sectionType":"part","heading":"9/2006","content":"## 9/2006","sortOrder":3}],"analysis":{"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"The underlying report came from a Fokker 100 operator, but the Directive extends the corrective requirement to Fokker 50 (F27 Mark 050/0502) because the PSU panels are similar. The AD therefore broadens the affected fleet from the initially reported Fokker 100 to include Fokker 50 types (Background; final paragraph)."},"complexity_factors":["Technical specificity: applies only to Honeywell (Grimes) PSU P/N 10-1178-XX on F27 Mark 050 and 0502 aeroplanes (Applicability).","Procedure dependence: inspection and rectification must follow Fokker Service Bulletin SBF50-25-061 or a later EASA‑approved revision, requiring operators to obtain and apply that external document (Requirement 1).","Timing and operational constraint: inspection required within 36 months; any discrepancies must be fixed before further flight, which can impose immediate operational interruption if defects are found (Compliance; Requirement 2).","Remedial uncertainty: the Directive calls for rectification of 'any discrepancies' which may range from minor adjustments to replacement of gaskets or panels, affecting parts, labour and scheduling (Requirement 2; Background).","Regulatory cross-reference: refers to CAA‑NL AD NL‑2006‑008 and EASA approval, so compliance and acceptable methods depend on those prior determinations (Note; Background).","Administrative discretion: acceptance of 'later EASA approved revision' creates a moving target for which revision to follow and when, requiring operators to track approvals (Requirement 1).","Supply/implementation risk: manufacturer changed gasket tolerances; availability of corrected gaskets or approved replacement parts may affect how quickly operators can rectify faults (Background)."],"plain_english_summary":"This Directive requires operators of Fokker F27 Mark 050 and 0502 aeroplanes fitted with Honeywell (Grimes) Passenger Service Units (P/N 10-1178-XX) to inspect the PSU panel interface connectors and to fix any gasket/connector faults. Inspections must follow Fokker Service Bulletin SBF50-25-061 (or a later EASA‑approved revision) within 36 months; any discrepancies must be rectified before further flight. The measure addresses connector locking/tolerance issues that can cause overheating, arcing and smoke."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope. It targets a specific safety defect identified in PSU connectors on Fokker F50 aircraft and requires a targeted inspection and rectification. There is no evidence of scope creep; the directive remains focused on the original safety issue without expanding to unrelated systems or aircraft types."},"complexity_factors":["Single, specific aircraft type and part number range (P/N 10-1178-XX)","Only two requirements: inspect, then rectify if needed","Clear compliance deadlines (36 months for inspection, before next flight for repairs)","References one external technical document (Fokker Service Bulletin SBF50-25-061) but does not incorporate complex conditional logic","No nested exceptions, defined terms section, or cross-references to other legislation","Straightforward cause-and-effect: gasket tolerance issue → inspection required → fix if broken"],"plain_english_summary":"This AD orders operators of Fokker F50 (F27 Mark 050/0502) with Honeywell/Grimes PSUs (part numbers 10-1178-XX) to inspect and, if necessary, repair overhead Passenger Service Unit electrical connectors within 36 months. Loose gaskets can prevent proper connector locking, risking overheating, arcing and smoke in the cabin. Any defects must be rectified before the aircraft next flies."}},"importantCases":[],"_links":{"self":"/api/acts/ad-f50-95-passenger-service-units","history":"/api/acts/ad-f50-95-passenger-service-units/history","analysis":"/api/acts/ad-f50-95-passenger-service-units/analysis","conflicts":"/api/acts/ad-f50-95-passenger-service-units/conflicts","importantCases":"/api/acts/ad-f50-95-passenger-service-units/important-cases","documents":"/api/acts/ad-f50-95-passenger-service-units/documents"}}